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首页> 外文会议>AIAA/ASME/SAE/ASEE joint propulsion conference;AIAA propulsion and energy forum >Design-For-Reliability Considerations and Modeling for Liquid Propulsion Engines Starting from Conceptual Design
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Design-For-Reliability Considerations and Modeling for Liquid Propulsion Engines Starting from Conceptual Design

机译：从概念设计开始的液体推进发动机可靠性设计考虑和建模

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摘要

Reliability is often considered to be one of the most important launch vehicle requirements and design parameters. In many NASA and US Air Force launch vehicle studies, reliability assessment results become one of the necessary attributes to support configuration and design option down-selections. One of our early papers discussed a comprehensive set of reliability drivers related to launch vehicle liquid propulsion engine systems, and presented a reliability model that parametrically analyzes some of the key reliability parameters. This paper extends that reliability model by analyzing more reliability parameters including: engine-out switching reliability; engine component, subsystem and system inherent designed reliability; manufacturing, inspection and operation capability and human error effects on the system reliability. The paper focuses the discussion on design-for-reliability starting from vehicle and propulsion system feasibility study, concept exploration, and early design stages (conceptual and preliminary designs). For the inherent designed reliability modeling, this paper introduces a Complexity Index (CI) approach that correlates the inherent designed reliability to the engine complexity related to the engine configuration, structural and performance requirements. For the manufacturing, inspection, testing, operation capability and human error effects on the system reliability, an As-built/As-tested/As-used Effectiveness Index (AI) is defined to address the delta between the inherent reliability and real flight reliability. Both the CI and AI indexes evolve from an abstract level to a detailed design level as design and development progresses from feasibility study, conceptual exploration, architectural design, to conceptual design, detailed design, testing, and to flight certification. The use of these two indexes to guide design-for-reliability starting from architectural and conceptual design to the detailed design is discussed and illustrative examples are presented. With the enhanced reliability model and the design-for-reliability approach, a more reliable, safer and affordable liquid propulsion engine system can be developed.
机译：可靠性通常被认为是最重要的运载火箭要求和设计参数之一。在许多NASA和美国空军的运载火箭研究中，可靠性评估结果成为支持配置和设计选项下推选择的必要属性之一。我们的一篇早期论文讨论了与运载火箭液体推进发动机系统有关的一整套可靠性驱动程序，并提出了一种可参数化分析某些关键可靠性参数的可靠性模型。本文通过分析更多的可靠性参数来扩展该可靠性模型，这些参数包括：发动机熄火切换可靠性;发动机部件，子系统和系统固有的设计可靠性;制造，检查和操作能力以及人为错误对系统可靠性的影响。本文将重点讨论从车辆和推进系统可行性研究，概念探索以及早期设计阶段（概念设计和初步设计）开始的可靠性设计。对于固有的设计可靠性建模，本文介绍了一种复杂性指数（CI）方法，该方法将固有的设计可靠性与与发动机配置，结构和性能要求相关的发动机复杂性相关联。对于制造，检查，测试，操作能力和人为错误对系统可靠性的影响，定义了已建成/已测试/已使用效率指数（AI），以解决固有可靠性与实际飞行可靠性之间的差额。随着设计和开发从可行性研究，概念探索，建筑设计，概念设计，详细设计，测试到飞行认证的发展，CI和AI索引都从抽象级别发展到详细设计级别。讨论了从建筑和概念设计到详细设计的这两个指标的使用，以指导可靠性设计，并给出了说明性示例。利用增强的可靠性模型和可靠性设计方法，可以开发出更可靠，更安全和负担得起的液体推进发动机系统。

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